Buoyant aeroplane



April 1932- M. M. AJBABULA 1,853,653

BUOYANT AEROPLANE Filed July 10, 1951 2 Sheets-Sheet l JNVENTOR BY H ATTORNEY m Patented Apr. 12, 1932 UNITED STATES PATENT OFFICE- BUOYANT AEROPLANE Application filed July 10, 1931. Serial No. 549,882.

This invention relates to improvements in aeroplanes, particularly in monoplanes of the lighter than air type, and it is the principal object of my invention to provide an aeroplane the fuselage and wings of which are divided in a plurality of compartments partly for the reception of the fuel such as gasolene and for the greater part for the reception of a gas which is lighter than air such as helium gas possessing such buoyancy as to stabilize and carry the aeroplane, each. of

the compartments can be filled separately and they are arranged in staggered relation so that a leak or damage to one compartment will not afl'cct the others.

Another object of my invention is the provision of an aeroplane of the lighter than air type the wings of which are made; integrally with its fuselage and the upper faces of the wings are so shaped as to prevent the accumulation of snow and ice thereon which will slide oil? the same.

A further object of. my invention is the provision of wings for an aeroplane of the lighter than air type each wing divided into an upper and lower compartment which in turn are sub-divided into longitudinal chambers, each of which is again sub-divided by transversal and staggered partitions into a plurality of compartments in such manner that the larger chambers of the lower compartment are oppositely disposed to the smaller chambers of the lower compartment, and vice versa.

A still further object of my invention is the provision of an aeroplane of the lighter than air type which is comparatively simple in its construction, yet compact and durable so that the wings cannot accidentally become separated from the fuselage and equipped witha propeller opening a straight path for the aeroplane.

These and other objects and advantages of my invention will become more fully known as the description thereof proceedsand will then bespecifically defined in the appended claim.

In the accompanying drawings forming a material part of this disclosure:

Fig. 1- is a top plan view of an aeroplane constructed according to my invention.

Fig. 2 is a front elevation thereof.

Fig. 3 is a side elevation of the areoplane.

Fig. 4 is a section through the same on line l4= of Figure 1.

Fig. 5 shows in detail perspective View. the interior arrangement of the cells in a wing.

As illustrated, the areoplane preferably of the monoplane type, has its wings 10, 11, made in one piece with the fuselage 12 and substan tially at an angle of about 45 thereto. At their ends the wings are equipped with ailerons 13, 14 of approved construction.

The fuselage is equipped with a front starting and landing gear of a conventional type generally designated 15, and a rear landing gear 16.

The customary vertical rudder 17, and hor- I izontal rudder 18 allows the steering of the aeroplane, while a motor operated propeller 19 is used for the propulsion of the areoplane and so arranged as to cut the air along a path designated by'suitable lilies in Figure 1.

According to my invention the fuselage is divided by suitable partitions 20 into a plurality of compartments 21 principally for the reception of gasoline or similar fuel and helium gas. The wings are each divided by a substantially horizontal transversally ar- 30 ranged partition 22 into upper and lower compartments, which in turn are divided by a longitudinally extending partition wall 23 into two compartments. Each of these compartments is again sub-divided by a plurality as of partitions 24, 25. arranged in staggered re-' lation into a plurality of compartments, preferably of a total number of 30 to be filled with helium gas separately so that if one of the compartments leaks its gas, it will not affect the others. The outer slanting form of the wings is such that snow or ice will never stay on top of the wings. I

The partitions dividing the upper compartment and the partitions dividing the lower compartment are arranged in staggered relation so that the larger compartments in the upper row are arranged oppositely to the smaller compartments in the lower .row and vice verse. 10!? for dividing said chambers into larger and It will be understood that I have described and shown the preferred form of my aeroplane only, and that I may make such changes in the construction of its minor details as come within the scope of the appended claim Without departure from my invention.

Having thus described my invention what I claim as new and desire to secure by Letters Patent is 1 In an aeroplane, wings, a horizontal partition for dividing each wing into an upper and lower compartment, a longitudinally extending partition separating said upper and lower compartments into chambers, and transverse partition walls in said upper and lower compartments in staggered relation to each other smaller oppositely disposed chambersfor the reception of a buoyant gas.

In witness whereof I have signed my name to this specification.

MACIEJ M. A. BABULA. 

